CN115922243A - Machining process for inner cavity of aircraft engine case - Google Patents

Abstract

The invention relates to the technical field of machining, and discloses a machining process for an inner cavity of an aeroengine case, wherein the inner cavity of the case comprises a plurality of bosses, each boss is provided with a ring groove, the boss at the opening end of the case and the boss partially positioned in the depth of the inner cavity are provided with vertical holes penetrating through the bosses on the back of the ring grooves, and part of the vertical holes are superposed with the ring grooves; inclined holes communicated with the annular grooves are formed in the back faces of the annular grooves on part of the bosses, and part of the inclined holes are formed in the edge of the inner cavity of the casing; through holes communicated with the annular grooves are formed in the back faces of the annular grooves on part of the bosses, and the diameter of each through hole is smaller than the width of each annular groove; the vertical hole, the inclined hole and the through hole are processed in a numerical control mode, a drill bit adopted for processing the vertical hole at the opening end of the casing is subjected to group drilling, a drill bit adopted for processing the through hole is subjected to group drilling and double-edged zone processing, and a drill bit adopted for processing the inclined hole and other vertical holes is provided with an internal cooling hole and is subjected to group drilling and double-edged zone processing. The process method can ensure that the size of each hole is qualified, saves labor and improves efficiency.

Description

Machining process for inner cavity of aircraft engine case

Technical Field

The invention relates to the technical field of thin-wall part machining, in particular to a machining process for an inner cavity of an aircraft engine case.

Background

In the parts of the aircraft engine, a plurality of parts need to be drilled and milled in the ring groove to play a role in ventilating or positioning the outer ring and the blade, such as parts of a turbine casing, a power turbine casing, a low-pressure turbine casing and the like.

Taking a certain type of turbine casing as an example, as shown in the attached figure 1 of the specification, the material is GH2132, the part is a ring-shaped part, the diameter of the large end is phi 674.8, the diameter of the small end is phi 605.5, the total length is 221.8mm, and the average wall thickness is about 2.8mm, and the part is a typical thin-wall part. The inner cavity of the part is provided with 7 bosses, the bosses are provided with ring grooves, and small holes are arranged in or near each groove, which totals 411; and 3 groups of mortises are distributed on 6 layers of bosses (each group of mortises is distributed on two adjacent layers of bosses), 23-27 mortises are arranged on each layer of bosses, each mortise is a chute with the width of 18-25 mm and the depth of about 2-6 mm, and the processing of the mortises is a pair of one-step processing of the mortises on the upper and lower layers of bosses.

Generally, the casing has a large space size, and the machining and inspection processes are complicated.

In fig. 1, the mounting edge of the small end of the casing has 92 phi 5.5 holes and the lower half circle of phi 3 holes at the 2 nd layer 46 of the small end are all half-edge holes (i.e. the holes have parts overlapped with the ring grooves); and the small end 3 rd layer and 5 th layer have 104 phi 3 holes, 1/4 turn of which is at the edge of the wall surface of the part, and the phi 2.6 holes at the 4 th layer and the 6 th layer 77 are both in the depth of the casing. At present, all the sizes (411) of small holes in the ring grooves are processed on a common drilling machine, so that the labor intensity of operators is high, and the processing efficiency is low; and the process route of the parts is long and tedious, so that the processing period is long and the production is tense. In addition, because the drilling worker is a manual process, the artificial low-level errors such as wrong hole drilling, deviated hole drilling, multiple hole drilling and the like are easily caused; such quality problems have also frequently occurred over the years, and the situation of wrong processing is high. The patent with publication number CN110497152A discloses a casing deep hole processing method and application thereof, in the technical scheme, the deep hole processing on the casing is still processed by a common drilling machine, and the problems can not be fundamentally solved.

The mortise is shown in figure 2, the mortise needs to be processed by using an angle head, the cutter is easy to wear due to difficult processing of materials, the angle head needs to be moved to perform cutter setting on the cutter setting instrument every time, the angle head is heavy and not easy to carry, so that a large amount of time is spent on cutter setting, the length of the tool is measured by the vernier caliper according to the characteristic of large dimensional tolerance (small dimensional tolerance is not applicable), and the quality problems of error in cutter setting measurement and the like exist.

The 3 groups of mortises are sequentially divided into an S1 group, an S2 group and an S3 group from the small end to the large end of the casing, the program is divided into rough machining and finish machining, and after the mortises are uniformly distributed at the 27 th group of the rough machining S3, the S2 group and the S1 group are processed. After all the mortises are roughly machined, finish machining is carried out, most of allowance is removed in the rough machining process of the mortises, the cutting force is large, and the reducing sleeve is easy to deform. Because the rough machining cutter is worn, the cutter needs to be replaced for finish machining, an operator cannot find that the reducing sleeve is deformed when the cutter is replaced, the hanging length of the cutter is measured by using the depth gauge after the cutter is directly replaced, and the actual hanging length of the cutter is larger than the measured value because the depth gauge is measured on the deformed reducing sleeve and the distance from the cutter point to the end face of the reducing sleeve cannot be accurately measured (see attached figure 3 in the specification). The bottom of the mortise is milled by a tool nose, the position of the tool nose is determined by measuring the hanging length value of the tool and inputting the value into a machine tool for compensation, so that the distance from the bottom of the mortise to the center is ensured, if the hanging length value of the measuring tool is smaller, the bottom of the mortise of the S3 group is over-cut, and the size from the bottom to the center is out of tolerance. Simultaneously every row of tongue-and-groove finish machining is same section procedure, and every section procedure all stops after the whole circle tongue-and-groove is processed, can not measure the size after processing every row of first department tongue-and-groove, fails in time to discover that the cutter hangs the length value and measures incorrectly, leads to whole circle groove depth ultratolerance.

Disclosure of Invention

The invention aims to overcome the defects of the prior art and provides a processing technology capable of improving the processing precision and the processing efficiency of various holes and mortises in an inner cavity of an aeroengine case.

The purpose of the invention is realized by the following technical scheme:

a processing technology for an inner cavity of an aeroengine casing comprises the steps that the inner cavity of the casing comprises a plurality of bosses, annular grooves are formed in the bosses, the bosses are located at the opening end of the casing, part of the bosses are located in the deep position of the inner cavity, vertical holes penetrating through the bosses are formed in the back face of the annular grooves, and part of the vertical holes are overlapped with the annular grooves; inclined holes communicated with the annular grooves are formed in the back faces of the annular grooves on part of the bosses, and part of the inclined holes are formed in the edge of the inner cavity of the casing; through holes communicated with the annular grooves are formed in the back faces of the annular grooves on part of the bosses, and the diameters of the through holes are smaller than the widths of the annular grooves; the aircraft engine casket inner chamber has been seted up the tongue-and-groove from last to down on a plurality of bosss in succession, and the tongue-and-groove uses per two-layer adjacent boss to be a set of processing, vertical hole, inclined hole and through-hole all adopt numerical control processing, and the brill sword drill bit that is located the vertical spot facing work adoption of aircraft engine casket opening end department is done the gang drill and is handled, the gang drill is done to the brill sword drill bit that the through-hole processing adopted and is handled with the twolip area, the cold hole is arranged and is done the gang drill and is handled with the twolip area in the brill drill bit setting that the processing of inclined hole and all the other vertical holes adopted.

Furthermore, the drill bit material is an ultra-fine hard alloy matched with a nano-scale TiALN coating.

Furthermore, the drill used for processing the through hole in the deep inner cavity of the casing is of an integral structure, the diameter of the neck of the drill is increased, and the drill point angle of the drill is 140 degrees.

Furthermore, the number of the internal cooling holes on the drill bit with the internal cooling holes is 1-2.

Further, the sequence of the vertical hole, the inclined hole and the through hole is as follows: firstly, processing a through hole in the deep part of the inner cavity, then processing a vertical hole at the opening end of the casing, then processing other vertical holes, then processing an inclined hole, and finally processing a through hole close to the opening end of the casing.

Furthermore, the total length of the drill for processing the inclined hole and the through hole is not less than 80mm, the suspension length is 50-53 mm, the processing linear speed is 20-25 m/s, and the feeding is 40-50mm/r.

Furthermore, the total length of the drill used for processing the vertical hole positioned in the deep part of the inner cavity is not less than 80mm, the suspension length is 56-58 mm, the processing linear speed is 20-25 m/s, and the feeding is 40-50mm/r.

Further, the machining life of the drill is designed to machine at least 2 casings per tool.

Further, the tool setting mode of tongue-and-groove processing does: and adding a tool setting position on a clamp for clamping the case, fixing a tool setting coordinate value on the clamp, and setting the tool by using a tool setting block.

Further, to the burr that inclined hole and annular link up the department mutually, design the burring frock, the burring frock includes the joint of being connected with the air gun of polishing and sets up the grinding rod on the joint, the groove that is used for pressing from both sides the material of establishing polishing is seted up to the grinding rod end, and the burring frock is rotated by the air gun control joint of polishing.

Compared with the prior art, the invention has the following beneficial effects:

each hole of the inner cavity of the casing is processed by the rotation control of the traditional common driller, and the numerical control processing combines multiple traditional procedures, thereby reducing the process route, greatly saving the processing time and improving the processing efficiency; meanwhile, by improving the cutter and optimizing the cutting parameters of the cutter, the problems of unstable drill bit processing, floating drill bit, poor cutter rigidity, poor cooling and chip removal effects and the like are effectively solved, and the qualification of the size processing of each hole is ensured;

aiming at the processing of the mortise, the tool setting mode is perfected, the distance L actual value from the circle center to the tool setting surface is marked above the tool setting position on the fixture, the dimension of the actual value of the fixture is determined, the tool setting value is ensured not to be influenced by the abrasion of the fixture, the operation that the angle head needs to be moved to carry out tool setting on the tool setting gauge when the tool is changed to set the tool in the prior art is omitted, the manpower is saved, and the efficiency is improved.

Drawings

FIG. 1 is a cross-sectional view of a casing according to the prior art and embodiments;

FIG. 2 is a schematic structural diagram of the mortise in the prior art and the embodiment;

FIG. 3 is a diagram of a measurement value of a tool overhang after deformation of a reducing sleeve in the background art;

FIG. 4 is a schematic structural view of a drill used for machining a vertical hole at an open end of a casing in embodiment 1;

FIG. 5 is a schematic structural view of a drill used for machining inclined holes and other vertical holes in example 1;

FIG. 6 is a schematic view showing the structure of a drill for forming a through-hole in example 1;

FIG. 7 is a schematic structural diagram of a tool setting perfecting mode on a fixture in embodiment 1;

fig. 8 is a schematic structural view of the burr grinding tool in embodiment 2;

fig. 9 isbase:Sub>A cross-sectional view taken along linebase:Sub>A-base:Sub>A of fig. 8.

Detailed Description

In order to clearly illustrate the technical features of the present solution, the following detailed description of the present solution is provided with reference to the accompanying drawings.

In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present application, however, the present application may be practiced in other ways than those described herein, and therefore the scope of the present application is not limited by the specific embodiments disclosed below.

In addition, in the description of the present application, it is to be understood that the terms "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "axial", "radial", "circumferential", and the like indicate orientations or positional relationships based on those shown in the drawings, merely for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be taken as limiting the present application. Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present application, "a plurality" means two or more unless specifically limited otherwise.

In this application, unless expressly stated or limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can include, for example, fixed connections, removable connections, or integral parts; the connection can be mechanical connection, electrical connection or communication; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.

In this application, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through intervening media. In the description of the present specification, reference to the description of "one embodiment," "some embodiments," "an example," "a specific example," or "some examples" or the like means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present application. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

The invention takes the structure of the aeroengine case in fig. 1 as an example, and provides a processing technology of the inner cavity of the case, as shown in fig. 1, the inner cavity of the case comprises a plurality of bosses 1, each boss is provided with a ring groove 2, the boss positioned at the opening end of the case and the boss partially positioned in the deep part of the inner cavity are provided with vertical holes 3 penetrating through the bosses on the back of the ring grooves, and part of the vertical holes 3 are superposed with the ring grooves 2; inclined holes 4 communicated with the ring grooves are formed in the back faces of the ring grooves 2 on part of the bosses, and part of the inclined holes 4 are formed in the edge of an inner cavity of the casing; through holes 5 communicated with the annular groove are formed in the back of the annular groove 2 on part of the bosses, and the diameter of each through hole 5 is smaller than the width of the annular groove 2; the mortise 6 (the mortise structure is shown in figure 2) is formed on a plurality of continuous bosses in the inner cavity of the casing from top to bottom, and each two layers of adjacent bosses are used as a group for processing the mortise.

Example 1

In this embodiment, the above-mentioned vertical hole, inclined hole and through hole of the casing are all processed by numerical control, but the following difficulties exist for the casing of this embodiment when the conventional numerical control method is used for processing:

1) When a common twist drill made of material M42 and hard alloy is used for processing a vertical hole of a casing, the condition of bit drifting is easy to occur due to uneven stress;

2) In a phi 2.6 through hole and a phi 3 inclined hole in the depth of the casing, particularly 1/4 circle of the phi 3 inclined hole is arranged at the edge of the wall surface of a part (namely the joint position of an inclined plane and a straight plane), the cutter has longer overhang and poorer rigidity during processing, and the condition of unstable centering also exists;

3) The holes are positioned at the annular groove of the casing, and the drill bit is easy to extrude and shake during machining due to unsmooth chip removal;

4) During machining, feeding cannot be adjusted through cutting resistance, and a process gasket cannot be adjusted manually during machining.

In the embodiment, in order to enable the casing to be successfully processed on the numerical control equipment, the drill for processing each hole is improved as follows:

as shown in FIG. 4, a drill bit used for processing the phi 5.5 vertical hole 3 at the opening end of the casing is subjected to group drilling. Compared with the common drill, the gang drill has the advantages that the gang drill grinds the chisel edge short, the average front angle is increased, the drilling is light and fast, the axial resistance is reduced by 30-52 percent, the drilling torque is reduced by 12-32 percent, the centering force can be well improved, the drilling force is reduced, the chip dividing and chip removing effects are good, the drilling is smooth, the friction is reduced, the cutting fluid can easily enter a cutting area, the cooling and lubricating effects are good, and the drilling temperature is low; the advantages effectively solve the problems of instability and drifting of the drill bit in the process of machining the drill bit and ensure that the aperture size of the phi 5.5 vertical hole of the part is all qualified.

As shown in fig. 5, the drill bit used for processing the inclined holes 4 and the vertical holes 3 in the third and fifth steps of the casing is provided with internal cooling holes (not shown) and is subjected to gang drilling and double-edged strip processing, the number of the internal cooling holes on the drill bit is generally designed to be 1-2, and the paths of the internal cooling holes are consistent along the path of the spiral groove of the drill bit. Because of the position of the vertical hole of phi 3 in the quick-witted casket is darker, the inclined hole is at part wall edge, adds the rigidity poor man-hour, and the drill bit wafts easily, and chip removal and cooling effect are poor, therefore the aforesaid is handled the ni zhifu brill that the drill bit was done, the twolip area is handled and is set up the interior cold bore and can bring a great deal of advantage: the vent groove that interior cold hole was passed for cutting fluid when cutting processing plays the cooling cutter effect, and the iron fillings that stick the sword through can washing away from this department are followed to the coolant liquid simultaneously, reduce cutter cutting temperature to make the cutting process more stable, effectual solution drill bit is floated, the cutter rigidity is poor, the problem of cooling and chip removal effect difference, guaranteed that the aperture size of part phi 3 vertical hole and inclined hole is whole qualified.

As shown in figure 6, the drill bit of the drill cutter for processing the through hole 5 is used for group drilling and double-edged belt processing, so that the chip removal function of the drill bit is increased, and the problems of unsmooth chip removal and poor rigidity during the processing of the drill bit are solved. Because the phi 2.6 through hole is in the deep of the casing, if the diameter of the drill bit handle is too large, the part can be obstructed, the hanging length is too long, and the rigidity of the cutter is poor, the drill bit at the position is changed into an integral type from a welding type, the diameter of the neck of the drill bit is increased at the position where the part is not obstructed, so that the rigidity of the drill bit is ensured, meanwhile, the angle of the drill bit tip of the drill bit is 140 degrees, the strength of the drill bit is increased, and the qualified aperture size of the phi 2.6 through hole is effectively ensured.

All the drill bit materials are ultra-fine grain hard alloy matched with a nano TiALN coating, so that the hardness of the drill bit reaches HRA92.1, and the drill bit is endowed with strong wear resistance and cutting performance.

The sequence of the processing technology for processing the vertical hole, the inclined hole and the through hole is as follows: firstly processing a phi 2.6 through hole in the deep part of the inner cavity, then processing a phi 5.5 vertical hole at the opening end of the case, then processing a phi 3 vertical hole, then processing a phi 3 inclined hole, and finally processing a phi 2.6 through hole close to the opening end (the large end of the case) of the case. Wherein the total length of the drill for processing the phi 3 inclined hole and the phi 2.6 through hole is not less than 80mm, the suspension length is 50-53 mm, the processing linear speed is 20-25 m/s, and the feeding is 40-50mm/r. The total length of the drill used for processing the phi 5.5 vertical hole positioned in the deep part of the inner cavity is not less than 80mm, the suspension length is 56-58 mm, the processing linear speed is 20-25 m/s, and the feeding is 40-50mm/r. The drill life is designed to process at least 2 cartridges per tool.

The following is a comparison between the above-mentioned hole machining process flow and the conventional machining process flow of the cartridge in this embodiment:

as can be seen from the above table, the present invention combines a plurality of processes by changing the common driller into numerical control processing.

Example 2

In this embodiment, on the basis of embodiment 1, a tool setting manner for tongue-and-groove machining is improved, specifically, a tool setting position is added to a fixture for clamping a casing, a tool setting coordinate value is fixed to the fixture, and a tool setting block is used for setting a tool.

As shown in fig. 7, a distance L from the center of the circle to the tool setting surface is marked above the tool setting position on the fixture, and the actual value of the fixture is subjected to fixed inspection, so that the tool setting value is ensured not to be influenced by the abrasion of the fixture. The problems of labor consumption and low efficiency caused by the fact that the angle head needs to be moved to carry out tool setting on the tool setting gauge each time are effectively solved.

When the tool is worn and the tool is changed, firstly the worn tool is dismounted, a new numerical control milling cutter is mounted according to the requirement of numerical control adjustment tool clamping overhanging, the tool edge is perpendicular to the + X axis of the machine tool by using the alignment gauge to support the straight fixture (the alignment fixture and the part center are consistent with the program G54 before processing), then the angle head with the new tool is moved to the tool edge designed by the fixture, and the tool is quickly adjusted by using the tool adjusting tool (the same number of lathes are used for tool adjustment). When the clamp is designed, the distance from the opposite edge to the center of the clamp and the distance from the center of the angle head to the bottom edge of the cutter are required to be ensured to be less than the distance of the rotation center of the machine tool. Otherwise, the bed will report the overtravel warning when the tool is set. The fixed coordinate value (actual value of branding on the clamp, need to be checked) and the size of the feeler block are inputted into the compensation of correspondent tool in the machine tool, then the machine tool can be continuously worked

Example 3

The processing of the intersection of the inclined hole and the annular groove on the casing is easy to generate residual burrs, the visual observation is inconvenient, a flashlight needs to be used for short-distance observation, common bench workers (a grinding screwdriver, a grinding wheel head, a diamond pen, a grinding wheel piece and the like) cannot stretch into the inclined hole to be removed, and the burrs cannot be removed easily during the removal; in addition, under the condition of sharp tool, parts are easy to damage, and appearance defects of the parts are caused.

This embodiment designs a burring frock to above-mentioned problem, as shown in fig. 8 and fig. 9, according to the drill bit structure of this intersection position of processing, reform transform, the burring frock includes the joint 71 of being connected with the air gun of polishing and sets up the pole 72 of polishing on connecting, pole 72 end is polished and is offered a length 17mm groove 73, be used for entangling fine sand paper (the material of polishing promptly), joint 71 connects the bench worker and polishes the air gun interface, the burring frock is rotated by the control of the air gun of polishing, fine sand paper gets rid of intersection department's burr at rotatory in-process, fine sand paper can also play the effect that the protection machine casket did not receive the instrument to damage.

Compared with the traditional processing method, the processing technology has the advantages that the processing time of a single part of the part can be shortened from 84.38 hours to 56.9 hours through statistics by combining the working procedures, reducing the process route, converting the common working procedure into numerical control for processing each hole, optimizing the cutting parameters, improving the tool setting method for processing the tongue-and-groove, and the like, and the processing quality of the part is effectively improved, and the processing qualified rate of the part is improved from 93.2% to 99.5%.

It should be understood that the above examples are only for clearly illustrating the technical solutions of the present invention, and are not intended to limit the embodiments of the present invention. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. This need not be, nor should it be exhaustive of all embodiments. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention should be included in the protection scope of the claims of the present invention.

Claims (10)

1. A processing technology for an inner cavity of an aeroengine casing comprises the steps that the inner cavity of the casing comprises a plurality of bosses, annular grooves are formed in the bosses, the bosses are located at the opening end of the casing, part of the bosses are located in the deep position of the inner cavity, vertical holes penetrating through the bosses are formed in the back face of the annular grooves, and part of the vertical holes are overlapped with the annular grooves; inclined holes communicated with the annular grooves are formed in the back faces of the annular grooves on part of the bosses, and part of the inclined holes are formed in the edge of the inner cavity of the casing; through holes communicated with the annular grooves are formed in the back faces of the annular grooves on part of the bosses, and the diameter of each through hole is smaller than the width of each annular groove; the casing inner chamber has been from last to having seted up the tongue-and-groove down on a plurality of continuous bosss, and the tongue-and-groove uses per two-layer adjacent boss to process as a set of, its characterized in that, vertical hole, inclined hole and through-hole all adopt numerical control processing, and the brill sword drill bit that the vertical spot facing work that lies in casing opening end department adopted is done the gang drill and is handled, the brill sword drill bit that the through-hole processing adopted is done the gang drill and is handled with the twolip area, the cold hole is arranged and is done the gang drill and is handled with the twolip area in the brill drill bit setting that the processing of inclined hole and all the other vertical holes adopted.

2. The process for machining the inner cavity of the aero-engine case according to claim 1, wherein the drill bit material is a superfine cemented carbide with a nanoscale TiALN coating.

3. The process for machining the inner cavity of the aeroengine case according to claim 1, wherein a drill used for machining the through hole deep in the inner cavity of the case is of an integral structure, the neck of the drill is thickened, and the drill point angle is 140 degrees.

4. The machining process for the inner cavity of the aero-engine case according to claim 1, wherein the number of the internal cooling holes on the drill bit with the internal cooling holes is 1-2.

5. The machining process of the inner cavity of the aero-engine case according to claim 1, wherein the sequence of the vertical hole, the inclined hole and the through hole is as follows: firstly, processing a through hole in the deep part of the inner cavity, then processing a vertical hole at the opening end of the casing, then processing other vertical holes, then processing an inclined hole, and finally processing a through hole close to the opening end of the casing.

6. The aeroengine case inner cavity processing technology of claim 1, wherein the total length of the drill used for processing the inclined hole and the through hole is not less than 80mm, the overhang length is 50-53 mm, the processing linear velocity is 20-25 m/s, and the feeding is 40-50mm/r.

7. The process for machining the inner cavity of the aero-engine case according to claim 1, wherein the total length of drill bits for machining the vertical hole deep in the inner cavity is not less than 80mm, the overhang length is 56-58 mm, the linear speed of machining is 20-25 m/s, and the feed is 40-50mm/r.

8. The aircraft engine case internal cavity machining process of claim 1, wherein the machining life of the drill is designed to machine at least 2 cases per cutter.

9. The machining process of the inner cavity of the aero-engine case according to claim 1, wherein the tool setting mode of the mortise machining is as follows: and adding a tool setting position on a clamp for clamping the casing, fixing a tool setting coordinate value on the clamp, and setting the tool by using a tool setting block.

10. The aircraft engine casing inner cavity machining process according to claim 1, characterized in that a deburring tool is designed for burrs at the through part of the inclined hole and the ring groove, the deburring tool comprises a connector connected with a polishing air gun and a polishing rod arranged on the connector, a groove used for clamping a polishing material is formed in the tail end of the polishing rod, and the deburring tool is controlled by the polishing air gun to rotate through the connector.

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